Heat transfer near injection hole by shock and boundary layer interaction in the supersonic flow field

Namkyu Lee, Jiwoon Song, Ji Yeul Bae, Yoon Goo Kang, Heecheol Ham, Ju Chan Bae, Hyung Hee Cho

Research output: Contribution to conferencePaper

Abstract

The flow structure and heat transfer coefficient are investigated using both experimental and numerical methods in the supersonic flowfield with transverse jet injection. The geometry of this research is an expansion nozzle with injection hole. The diameter of injection jet hole is 8.8 mm. The supersonic flow facility used in this research is the intermittent supersonic blow down tunnel. The expansion ratio of nozzle (A/A∗) has 4.23 at the outlet and 3.56 at the injection location. Selected jet-to-freestream momentum flux ratio is J = 0.5, 1.0 and 1.3 to verify the variation related to the momentum ratio near J = 1.0 which is common momentum ratio for secondary injection system. Flow structure with shock interaction at the surface is visualized by oil-lampblack and numerical simulation. Heat transfer on the surface is measured by IR thermography using transient method. Results show that the first separation point moves to the adverse direction of flow with increasing jet-tofreestream momentum ratio. Also, the peak value of heat transfer increases and moves farther from jet location due to penetration of transverse jet. These results will serve as fundamental database for thermal design of transverse jet.

Original languageEnglish
Publication statusPublished - 2014 Jan 1
Event15th International Heat Transfer Conference, IHTC 2014 - Kyoto, Japan
Duration: 2014 Aug 102014 Aug 15

Other

Other15th International Heat Transfer Conference, IHTC 2014
CountryJapan
CityKyoto
Period14/8/1014/8/15

Fingerprint

shock layers
supersonic flow
Supersonic flow
boundary layers
Flow fields
flow distribution
Boundary layers
heat transfer
injection
Heat transfer
Momentum
momentum
interactions
Flow structure
nozzles
secondary injection
Nozzles
expansion
outlets
heat transfer coefficients

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering
  • Condensed Matter Physics

Cite this

Lee, N., Song, J., Bae, J. Y., Kang, Y. G., Ham, H., Bae, J. C., & Cho, H. H. (2014). Heat transfer near injection hole by shock and boundary layer interaction in the supersonic flow field. Paper presented at 15th International Heat Transfer Conference, IHTC 2014, Kyoto, Japan.
Lee, Namkyu ; Song, Jiwoon ; Bae, Ji Yeul ; Kang, Yoon Goo ; Ham, Heecheol ; Bae, Ju Chan ; Cho, Hyung Hee. / Heat transfer near injection hole by shock and boundary layer interaction in the supersonic flow field. Paper presented at 15th International Heat Transfer Conference, IHTC 2014, Kyoto, Japan.
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Lee, N, Song, J, Bae, JY, Kang, YG, Ham, H, Bae, JC & Cho, HH 2014, 'Heat transfer near injection hole by shock and boundary layer interaction in the supersonic flow field' Paper presented at 15th International Heat Transfer Conference, IHTC 2014, Kyoto, Japan, 14/8/10 - 14/8/15, .

Heat transfer near injection hole by shock and boundary layer interaction in the supersonic flow field. / Lee, Namkyu; Song, Jiwoon; Bae, Ji Yeul; Kang, Yoon Goo; Ham, Heecheol; Bae, Ju Chan; Cho, Hyung Hee.

2014. Paper presented at 15th International Heat Transfer Conference, IHTC 2014, Kyoto, Japan.

Research output: Contribution to conferencePaper

TY - CONF

T1 - Heat transfer near injection hole by shock and boundary layer interaction in the supersonic flow field

AU - Lee, Namkyu

AU - Song, Jiwoon

AU - Bae, Ji Yeul

AU - Kang, Yoon Goo

AU - Ham, Heecheol

AU - Bae, Ju Chan

AU - Cho, Hyung Hee

PY - 2014/1/1

Y1 - 2014/1/1

N2 - The flow structure and heat transfer coefficient are investigated using both experimental and numerical methods in the supersonic flowfield with transverse jet injection. The geometry of this research is an expansion nozzle with injection hole. The diameter of injection jet hole is 8.8 mm. The supersonic flow facility used in this research is the intermittent supersonic blow down tunnel. The expansion ratio of nozzle (A/A∗) has 4.23 at the outlet and 3.56 at the injection location. Selected jet-to-freestream momentum flux ratio is J = 0.5, 1.0 and 1.3 to verify the variation related to the momentum ratio near J = 1.0 which is common momentum ratio for secondary injection system. Flow structure with shock interaction at the surface is visualized by oil-lampblack and numerical simulation. Heat transfer on the surface is measured by IR thermography using transient method. Results show that the first separation point moves to the adverse direction of flow with increasing jet-tofreestream momentum ratio. Also, the peak value of heat transfer increases and moves farther from jet location due to penetration of transverse jet. These results will serve as fundamental database for thermal design of transverse jet.

AB - The flow structure and heat transfer coefficient are investigated using both experimental and numerical methods in the supersonic flowfield with transverse jet injection. The geometry of this research is an expansion nozzle with injection hole. The diameter of injection jet hole is 8.8 mm. The supersonic flow facility used in this research is the intermittent supersonic blow down tunnel. The expansion ratio of nozzle (A/A∗) has 4.23 at the outlet and 3.56 at the injection location. Selected jet-to-freestream momentum flux ratio is J = 0.5, 1.0 and 1.3 to verify the variation related to the momentum ratio near J = 1.0 which is common momentum ratio for secondary injection system. Flow structure with shock interaction at the surface is visualized by oil-lampblack and numerical simulation. Heat transfer on the surface is measured by IR thermography using transient method. Results show that the first separation point moves to the adverse direction of flow with increasing jet-tofreestream momentum ratio. Also, the peak value of heat transfer increases and moves farther from jet location due to penetration of transverse jet. These results will serve as fundamental database for thermal design of transverse jet.

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M3 - Paper

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Lee N, Song J, Bae JY, Kang YG, Ham H, Bae JC et al. Heat transfer near injection hole by shock and boundary layer interaction in the supersonic flow field. 2014. Paper presented at 15th International Heat Transfer Conference, IHTC 2014, Kyoto, Japan.